Connection between the longitudinal and transverse bracing members in hollow bodies for aircraft



April 28, 1931 2 Sheets-Sheet 1 Filed July 15, 1929 w. MESSERSCHMITT-CONNECTION BETWEEN THE LONGITUDINAL AND TRANSVERSE BRACING. MEMBERS INHOLLOW BODIES FOR AIRCRAFT i 1931- w. MESSERSCHMITT 1,802,438 vCONNECTION BETWEEN THE LONGITUDINAL AND TRANSVERSE BRACING MEMBERS INHOLLOW BODIES FOR AIRCRAFT Filed July 15, 1929 2 Sheets-Sheet 2 PatentedApr. 1931 i UNITED STATES PKATEN'I. oFFica WIIJI JY- IISSERSCHMITT, OF AUGBBURG, GERMANY common BETWEEN TEE LONG-I'IU'DINAL AND TRANSVERSE.BBAGIIING- MEMBERS IN HOLL W BODIES FOR Application filed July 15,1929, Serial 1%.8'78395, and in Germany July 16, 1928.

This invention relates to a connection be- Figure 2 a construction ofthe new method tween the longitudinal and transverse bracof connection,

ing members in hollow bodies for aircraft. Figure 3 a second method ofmaking it,

One object of the invention is to improve a Figure 4 a third method indiagrammatic 5 and to simplify the connections of that kind form. H

hitherto employed. In the method which was formerly in gen- Accordingtothe invention, such a con'neceral use (compare Fi re 1), the securingtion is effected by providing the longitudinal was effected either byending the ribs a on bracing members, at the junction points bethelattice or sheet metal spar b and riveted,

w tween the same and the transverse bracing or riveted to previouslysecured angle irons members, with slots, and the transverse bracc. Theribs are also pushed as a whole over ing members with projecting lugswhich are the spar and connected to the same. The pushed through thecorresponding slots of chief drawbacks of this construction are that thelongitudinal bracing members and sethe ribs have to be secured to thespar before 15 cured at the side of the longitudinal bracing, theplating is effected. so which is opposite the transverse bracing. In theconstruction according to the inven- This securing at the opposite sideof the lontion illustrated in Figure 2, the longitudinal gitudinalbracing may be effected by bendspar b is provided atthe point where theing there the lugs ushed through and rivettransverse rib a is to besecured to it, with a 20 ing them to the a joining side of thelongivertical slot which passes right through the tudinal bracing. rspar metal plate 6'. The ri a is provided Inthe application to thebuilding-up of with a projecting lug a. which is so large aircraft wingsand guide surfaces, the arthat it can just be pushed through the slotrangement could be made so that the ribs of b. The securing of the partstogether in 25 the aircraft wings or guide surfaces are protheconstruction according to Figure 2 convided with lugs which are pushedthrough sists in angle irons 0, a being arranged on the one or moreslots in the' spar-plate and 'seface of the spar b away from the rib aat cured to angle irons laterally arranged on both sides of the slot andriveted with one the spar. The slots inthe spar plate may exflange tothe spar plate I) and with the tend from top to the bottom or be limitedonly other to the lug a of the rib a V to a short length, and the ribsmay also be In the construction according to Figure 3, built up ofparts. the lug is subdivided by horizontal cutsinto A special advantageof the construction several single lugs a" and a'" which are describedis that the singleparts of the airturned to both sides flat against thespar 35 craft wings or other hollow spaces such as plate I)" and securedto it by rivets (Z. for instance a completely covered or plated In theconstruction according to Fi ure 4, tip rib box can be placed at once onthe spar the spar is provided with several s ots b and connected to-it.through which are passed the tooth shaped Several constructionsaccording to the inlugs a. They can be secured in the same 0 vention areshown by way of example inthe way as in the constructions according to35 v accompanying in which: Fi re 2 and Figure 3.

Figure 1 shows the manufacture of such a p at I claim is:' y

' connection between the lon 'tudinal' and Aconnection between thelongitudinal and transverse bracing members 0 the formerly transversebracipvgnmembers in hollow bodies 45 usual kind, for aircraft, in 'chthe longitudinal brac- 9 member being g member is provided at thejunction with the transverse member with a slot, including angle ironsfixed on the longitudinal member ad acent the slot, the transversebracing rovided with a projecting lug ada ted 50%6 passed through thesai slot, an means to secure the projecting end of said lug to saidangle irons.

In testimony whereof I have signed my 01181118 to this sgecification.

Y MESSERSCHMITT.

